Space suit

ABSTRACT

Disclosed is a pressure suit for high altitude flights and particularly space missions. The suit is designed for astronauts in the Apollo Space Program and may be worn both inside and outside a space vehicle, as well as on the lunar surface. It comprises an integrated assembly of inner comfort liner, intermediate pressure garment, and outer thermal protective garment with removable helmet and gloves. The pressure garment comprises an inner convoluted sealing bladder and outer fabric restraint to which are attached a plurality of cable restraint assemblies. It provides versitility in combination with improved sealing and increased mobility for internal pressures suitable for life support in the near vacuum of outer space.

United States Pate [1 1 Shepard et al.

[ SPACE SUIT [75] inventors: Leonard F. Shepard; George P.

Durney; Melvin C. Case; A. J. Kenneway, Ill; Robert C. Wise; DixieRinehart, all of Dover; Ronald J. Bessette, Wyoming; Richard C. Pulling,Dover, all of Del.

References Cited UNITED STATES PATENTS Laubach 2/227 Krupp 2/2.l R

Dumey 2/2 Akerman.... 2/2.l X Lent et a1... 128/283 X Foti 2/2.l UX Hartet al.... 2/2.1 Krupp 2/2.l X White 2/2.1 X Colley..... 2/2.1 X Correale2/2.l

[ Aug. 1A, 1973 International Science and Technology Publication,February 1967 (page 33 relied on), by M. l. Radnofsky PrimaryExaminer-Jordan Franklin Assistant Examiner-George l-l. KrizmanichAttorney-Leonard Rawicz, Neil B. Siegel and Marvin F. Matthews [5 7]ABSTRACT Disclosed is a pressure suit for high altitude flights andparticularly space missions. The suit is designed for astronauts in theApollo Space Program and may be worn both inside and outside a spacevehicle, as well as on the lunar surface. It comprises an integratedassembly of inner comfort liner, intermediate pressure garment, andouter thermal protective garment with removable helmet and gloves. Thepressure garment comprises an inner convoluted sealing'bladder and outerfabric restraint to which are attached a plurality of cable restraintassemblies. It provides versitility in combination with improved sealingand increased mobility for internal pressures suitable for life supportin the near vacuum of outer space.

11 Claims, 25 Drawing Figures United Stat e s Patent [1 1 [11 3,751,721

Shepard et al. Aug. M, 1973 PATENIED M I 4 975 SHEET 01 0F 10 INVENTORSLEONARD E SHEPARD GEORGE DUR/VEY MEL w/v C, 5

A J. KE/VA/EWAY 1U ROBE/Pr C, 144

O/X/E L. R/A/EHART PAIENI we 1 4 ms SHEEI 03 0F 10 'FIG.'3

PATENIEU I 41975 3. 751 .72 7

saw on or 10 Pmmrmwm 4 ma 7 51 7 sum as or 10 PAIENIED M18 I 41975 sum10 0F 1 SPACE SUIT ORIGIN OF INVENTION The invention described hereinwas made in the performance of work under a NASA contract and is subjectto the provisions of Section 305 of the National Aeronautics and SpaceAct of 1958, Public Law 85-568 [72 Stat. 435, 42 U.S.C. 2457].

This invention is directed to a pressure suit to be worn by human beingsin a hostile environment, and

more particularly is directed to a life support suit to be worn by US.astronauts in the Apollo Space Program. The suit is designed to providelife support not only within a space vehicle, but also duringextravehicular activities including exploration of the lunar surface. Itmay also be used by aircraft pilots during high altitude flights.

The suit of the present invention, in conjunction with a unit strappedto the astronauts back, is believed for the first time to provide acompletely self-sustaining system which for a limited period of timeenables the astronaut to freely perform extravehicular activities, suchas external spacecraft corrective maintenance and lunar surfaceexploration. A primary feature of the space suit of this inventioninvolves the retention of a pressurized atmosphere about the astronautin the vacuum of free space, while at the same time providingsignificantly increased mobility, both in the torso and the limbs, sothat the astronaut may freely move about and perform useful tasks. Atthe same time, the suit incorporates novel constructions and assembliesfor permitting normal body functions, maintains a breathable atmosphereabout the astronaut controlled both as to pressure and temperature, andaffords significant protection from micro-meteroids and other physicaldangers the astronaut may encounter.

The suit comprises, as the principal componennan integratedthree-garment assembly comprising an inner comfort linear, anintermediate pressure garment assembly providing a controlled atmospherewithin the garment without excessively inhibiting astronaut mobility,and an outer insulating and protective layer referred to as anintegrated thermal micrometeoroid garment. These three garments areintegrally joined and are of anthropomorphic construction individuallyfitted to accommodate the dimensions of each astronaut. They aredesigned to cover the entire body in conjunction with removable glovesand a removable helmet. The suit of the present invention is worn overspecially designed undergarments which cooperate with the suit,including helmet and gloves, to completely support normal lifefunctions.

Versatility is built into the suit such that with a minimum ofinterchangeable parts the suit can be readily adapted to completelydifferent astronaut missions. This versatility also makes possibleincreased comfort for an astronaut during a mission since it not onlymakes it possible for the astronaut to select the most comfortable andsuitable combination for his particular task but certain elements of thespace suit may be completely removed for increased comfort during timeswhen they are not needed. For example, both the gloves and helmet arecompletely removable and may be taken off by the astronaut within thepressurized cabin of a space vehicle when it is not necessary to rely onthe suit for life support. Finally, the suit is provided with aredundant pressurized life support gas connection for increased safety.All of this is incorporated in a unit which when completely assembledhas a total weight, including helmet and protective shield, of only alittle over pounds.

-It is therefore one object of the present invention to provide animproved space suit particularly designed to be worn by astronauts inthe Apollo Space Program.

Another object of the present invention is to provide a pressurized suitand an associated assembly adapted to be worn by astronauts and highaltitude aircraft personnel in a hostile and particularly low pressureenvironment.

Another object of the present invention is to provide a space suitparticularly adapted with a minimum of modification for bothintravehicular and extravehicular use and particularly designed tosupport human life during exploration of the lunar surface.

Another object of the present invention is to provide an improvedpressurized space suit having improved gas sealing qualities and at thesame time providing optimum mobility for the wearer.

Another object of the present invention is to provide a pressurizedspace suit assembly particularly designed to be completelyself-contained for sustaining human life independent of any other lifesupport source for periods of several hours. The suit is adapted toexisting interface equipment and during intravehicular activity may becompletely interfaced with the cabin life support system of a spacevehicle.

These and further objects and advantages of the invention will be moreapparent upon reference to the following specification, claims, andappended drawings, wherein:

FIG. 1 is a perspective view of the overall space suit and associatedlife supporting unit as provided for extravehicular activity andparticularly lunar surface exploration;

FIG. 2 is a perspective view similar t o FIG. 1 showing the suit alone,with extravehicular overshoes, gloves,

and a helmet shield removed;

FIG. 3 is an exploded view showing the major components making up theextravehicular configuration of the space suit and undergarmentconstruction of the present invention;

FIG. 4 is an exploded view similar to that of FIG. 3 showing the majorcomponents of the suit usable for intravehicular activities;

FIG. 5 is an enlarged perspective view of the suit with helmet andgloves removed and the integrated thermal micrometeoroid garment omittedfor the sake of clary;

FIG. 6 is an enlarged view showing the thigh and upper right leg portionof the basic pressure garment assembly of FIG. 5;

FIG. 7 is a perspective view of the inner liner for the pressuregarmentassembly of FIG. 5;

FIG. 8 is a perspective view of the helmet neck ring for the space suitof this invention;

FIG. 9 is a similar perspective view of the suit neck ring adapted to beattached to the helmet neck ring of FIG. 8;

FIG. 10 is a perspective view of the transparent pressure helmetassembly for the space suit of the present invention;

FIG. 11 shows the space suit electrical harness;

FIG. 12 is a perspective view showing the rear portion of the outergarment or integrated thermal micrometeoroid garment of the space suit;

FIG. 13 is a perspective view of one of the pressure gloves of the spacesuit;

FIG. 14 is a perspective view of an extravehicular glove adapted to beworn over the glove of FIG. 13 during extravehicular activities;

- FIG. 15 is a perspective view of the left lunar overshoe for the suitof the present invention;

FIG. 16 is a perspective view similar to that of FIG. 15 of the rightlunar overshoe;

FIG. 17 is a perspective view with enlarged pertinent cross sections(17A,l7B,l7C) showing the extravehicular visor assembly of the spacesuit;

FIG. 18 is a perspective view showing an undergarment usable in theextravehicular configuration, i.e., the liquid cooling garment;

FIG. 19 is a perspective view of the pressurization and ventilation lifesupport pressure gas system for the suit of the present invention;

FIG. 20 is a perspective view of one of the locking rings at each wristof the suit;

FIG. 21 is a similar view of a locking ring mounted on one of the glovesand adapted to lock to the wrist ring of FIG. 20; and

FIG. 22 is a schematic cross sectional plan view through the torso andright wrist portion of the suit taken along line 22-22 of FIG. 2.

Referring to the drawings, the self-contained life supporting system ofthe present invention is generally indicated at in FIG. 1 andillustrates how the astronaut will appear as he explores the surface ofthe moon. The system of FIG. I is designed to permit the astronautsubstantial mobility and to make him completely selfsustaining forperiods of as much as 6 hours or more outside the space vehicle andparticularly on the lunar surface.

The assembly 10 comprises as its major component a space suit, generallyindicated at 12, to the back of which is strapped a lunar module 13including an oxygen purge system, generally indicated at 14, and aportable life support system beneath it containing water, filters,battery, etc., is generally indicated at 16. Communication with otherastronauts and with the space ship is maintained by way of an antenna18.

As illustrated in FIG. 1, the suit 12 comprises a re movable helmet overwhich is mounted an extravehicular visor assembly 20 to protect theastronaut both from physical injury or damage and from the intense raysof the sun outside the space vehicle. Mounted on the astronaut's upperchest is a portable life support system control box 22 which isconnected by line 24 to the oxygen purge system 14 and by a second line26 to the portable life support system 16, both mounted by straps on theastronaut's back. During extravehicular activity, the suit isperiodically purged by the astronauts manual operation of an oxygenpurge system actuator 28, mounted on the control box 22. Oxygen flow tothe interior of the suit is by way ofa system umbilical 30 whichconnects from the oxygen purge system 14 to the chest ofthe space suit12 in a manner more fully described below. The oxygen connections on thechest of the suit are closed off by a connector cover 32 in FIG. 1.Other connections to the apparatus mounted on the astronauts backproviding for communication, ventilation and liquid cooling are fromadditional connectors beneath cover 32 by way of umbilicals 34. Forextravehicular activity, the astronaut is provided with a pair ofextravehicular gloves 36 and 38 and a pair of lunar overshoes 40 and 42which cooperate to protect extremities from the hazards of space andparticularly provide protection by way of thermal insulation fromintense sunlight and provide physical protection from micro-meteoroidbombardment. The outer garment illustrated in FIG. I, referred to as theintegrated thermal micro-meteoroid garment, is a metallized white orlight colored fabric and is designed to provide thermal insulation andmicro-meteoroid protection.

The suit is provided with a plurality of pockets so that the astronautwill have ready access to everything that he may need outside thevehicle. Just below one shoulder of the space suit 12 is a sunglassespocket 44. A similar pocket 46 adjacent the other shoulder is a penlightpocket. A utility pocket 48 is provided in the upper left leg. Finally,the upper right leg of the integrated thermal micro-meteoroid garment orouter suit garment is provided with a flap 50 which not only houses thesuit donning lanyard, but also is an access flap for a urine collectionand transfer assembly, for a dosimeter connection, and includes aself-sealing patch for bio-medical injections.

FIG. 2 shows the astronaut as he might appear inside the space vehicleeither before or after extravehicular activity. In FIG. 2, the lunarmodule 13 has been removed from the astronaut's back, and helmet shield20 has been removed as have the extravehicular gloves and lunarovershoes. Also, the front chest cover has been removed to expose thevarious connectors for establishing fluid and electrical communicationto the interior of the suit.

Covering the astronauts head is a pressure helmet assembly 52 includinga shell formed of a transparent polycarbonate material. The helmet isattached to the neck of the suit by an interlocking metal ring assembly,generally indicated at 54, one ring of which is attached to the helmetand the other to the suit neck. A neck dam (not shown) may be insertedinto the neck of the suit to act as a water shield for re-entry or otherpurposes when it is believed that the astronaut may land in the ocean orotherwise be exposed to a water environment.

In FIG. 2, the connector cover is removed exposing four gas connectionscomprising two upper inlet connections 56 and 58 and two lower outletconnections 60 and 62. These connections permit life support gas, suchas oxygen, to be passed into and out of the space suit which (1)provides oxygen for the astronaut to breath, (2) maintains the interiorof the suit pressurized, and (3) provides ventilation over theastronaut's entire body. Connector 64 on the astronauts chest is forcirculating cooling liquid, such as water, through the interior of thespace suit which is only required during extravehicular activity, whileconnector 66 provides for electrical connection to the interior of thespace suit. Two of the lines passing through electrical connector 66lead to a pair of microphones 68 and 70 located adjacent the astronautsmouth by means of which he can communicate with other astronauts andwith communication equipment on board the space vehicle.

Removal of the extravehicular gloves 36 and 38 of FIG. 1 exposes in FIG.2 the pressure gloves 72 and 74. These gloves are formed in part from arubberized fabric and have sufficient flexibility so that the astronautcan perform a variety of intricate manipulations with the fingers andhands. Removal of the lunar overshoes 40 and 42 of FIG. 1 exposes inFIG. 2 the boots 76 and 78 which are formed integral with the remainderof the space suit. On the right-hand arm above glove 72 is a pressuregage 80 by means of which the astronaut is able to monitor the pressurewithin the suit and at approximately the same location on the left armis a pressure relief valve 82 adapted to open at a predeterminedpressure to automatically relieve the pressure within the suit when itbecomes too high. The suit is entered through a slide fastener or zipperpassing over the back from just beneath the neck downwardly between theshoulders and through the crotch to the front of the suit, whichfastener is covered by an entrance slide fastener flap 84. Finally,strapped to the astronauts legs are a scissors pocket 86, a checklistpocket 88, and a data list pocket 90.

FIG. 3 is an exploded view showing the elements of the space suit andundergarments of the present invention used for extravehicular activity.In addition to the suit proper, hereafter referred to as the pressuregarment assembly generally indicated at 12 in FIG. 3, the astronautwears beneath the pressure garment assembly a fecal containmentsubsystem 92 worn much in the manner of undershorts, a urine collectionand transfer assembly 94, a bio-medical belt 96, and a liquid coolinggarment 98 worn much in the manner of long underwear. The undergarments92, 94, 96, and 98 are normally donned by the astronaut in the order inwhich they'are numbered. Over the basic pressure garment assembly, theastronaut wears elements previously described, namely, theextravehicular visor assembly 20, connector cover 32, extravehiculargloves, such as glove 38, and lunar overshoes, such as overshoe 42. Thesuit is put on by the astronaut with the aid of a pair of removabledonning straps 100 and 102, which after the suit has been donned arestored beneath the access flap 50. Within the helmet 52, the astronaut'shead is surrounded by a communications carrier 104 on which are mountedthe microphones previously described.

FIG. 4 is an exploded view showing all the elements of the space suitforming the intravehicular configuration. That is, it is contemplatedthat at least one astronaut in the Apollo Program flights will remain inthe space vehicle at all times. This astronaut does not need theextravehicular protection of the others and for this reason may wear amodified suit of the same basic construction, but with importantmodifications. In FIG. 4, like parts bear like reference numeals, and itwill be noted that the intravehicular configuration of FIG. 4 is quitesimilar to the extravehicular configuration of FIG. 3. The principaldifference is that in place of the liquid cooling garment 98 illustratedin FIG. 3, the astronaut wears a constant wear garment 106 beneath thepressure garment 12 very closely resembling a pair of long underwear.The constant wear garment 106 is optional and the astronaut may, ifdesired, wear the liquid cooling garment 98 of FIG. 3 so that, in caseof an emergency, he too will be prepared to go outside the vehicle wherehe will be exposed to intensive sunlight and the liquid cooling providedby the garment 98 is required. FIG. 4 also shows various components ofthe basic pressure garment assembly, including the pressure helmetassembly 52 and pressure glove 72, previously described. Inside thevehicle, the astronaut may slip a cover glove assembly 108 over thepressure glove 72 to protect it and may slip a helmet shield 110 overthe pressure helmet assembly 52 to protect it from contact with theinside of the space vehicle. As previously mentioned, the basic pressuregarment assembly 12 comprises an outer garment 112, previously referredto as the integrated thermal micro-meteoroid garment, which is attachedto the pressure sealing and mobility providing garment, hereafterreferred to as the torso limb suit assembly 114. Communications carrier104 forms part of the torso limb suit assembly, whereas themicro-meteriod garment 112 is provided with a removable chest cover 116.

FIG. 5 is an enlarged perspective view of the torso limb suit 114 which,while shown separately, is worn integrally with an inner comfort linerdescribed below and the outer micro-meteoriod garment 112, previouslydescribed.

The torso limb suit 114 of FIG. 5 forms a basic component of the spacesuit of the present invention since, in conjunction with the helmet andgloves, it provides a life supporting environment for the astronaut and,more specifically, acts both as the pressure retaining sealing componentfor the suit and at the same time incorporates constructions andassemblies which provide for increased mobility. That is, when the spacesuit is inflated to an internal operating pressure in the neighborhoodof 3 to 4 pounds per square inch, the space suit tends to expand andbecome rigid so that it is difficult for the astronaut to move about. Inorder to increase the astronauts mobility, substantially constant volumebellows-like convolutes are provided at most of the suit joints andvarious cable and restraint assemblies are mounted to the exterior ofthe suit to permit the astronaut to bend and flex the suit joints andmove about. Pressure scaling is effected by providing the suit with aninner rubberized fabric layer referred to as a bladder 1 18, Over thebladder are several layers of fabric forming a restraint layer 1 19which protect the bladder and also aid in retraining it.

Referring to FIG. 5, the helmet attaching ring is illustrated at assecured to the neck of the space suit. A pair of covers 122 and 124overlie a pair of constant volume shoulder convolutes which permit theastronaut to flex and bend the shoulder joints without undue effort whenthe suit is inflated. Similar covers 126 and 128 overlie constant volumeconvolutes provided in the suit adjacent the elbow. Covered convolutesare also provided at the hips or upper thigh as illustrated at 130 and132 and at the knee joints as illustrated at 134 and 136.

Unless these constant volume convolutes are in some way restrained, theytend to elongate and expand under the internal pressure within the suit.Thus, the thigh convolute 167 is restrained against expansion by itscover 130 and is longitudinally restrained by a metal cable 168 attachedat its upper end to a reinforced portion of the suit at the hip and atits lower end to a reinforcing patch adjacent the knee which cable iscovered by a fabric wear sleeve or cable guide 138. It is understoodthat a similar cable provides restraint at hip joint 130 on the insideof the leg, as well as the outside, i.e., spaced about the astronautsleg approximately 180 from the cable 138.

The shoulder restraint takes the form of a shoulder cable which extendscontinuously from over the astronauts breast bone through the shoulderassembly adjacent convolute 122 across the astronauts back and backthrough the other shoulder assembly adjacent convolute 124 to a shouldercable disconnect 142. This cable restrains the shoulders and iscontinuous except for the two ends attached to the disconnect 142 whichthe astronaut, at his option, may open to disconnect cable 140 andremove the shoulder restraint should he so desire.

Additional restraint is provided by a crotch wire assembly, partlyillustrated at 144, which assists the astronaut in bending and othertorso movements. One end of the crotch cable assembly 144 is attached toa reinforcing patch l46 having a loop 148 adapted to receive straps forsupporting the lunar module 13 of FIG. 1. Lunar module support eyeletsare also provided at each hip as illustrated by the eyelet 150. Toassist the astronaut in bending forward and in sitting down, the frontof the torso is provided with a block and tackle assembly including atorso adjusting strip 152 which the astronaut may grasp and pull toforeshorten the torso of the suit and relieve forward bending stresseson his body. The upper end of this assembly is provided with an upperlunar module supporting bracket including an eyelet, generally indicatedat 154.

The space suit of the present invention is custom designed and fitted toeach astronaut. In order to provide fine adjustment for the astronautslimbs, portions of the arms and legs are joined by interlacing which maybe adjusted to slightly shorten or lengthen the limb portions of thesuit in accordance with the astronauts preferences. The lacing in thearms is just above the wrist connector rings 123 and 125, as 156 at 156,and 158, respectively. Similar lacings are illustrated at 160 and 162 inthe legs just above the boots 78 and 76. Formed in the right legs of thetorso suit 114 of FIG. and adapted to underlie the flap 50 of FIG. 1 isa urine transfer fitting 164 and a bio-medical injection patch 166. Thispatch comprises self-sealing rubber type material which may be puncturedby a hypodermic needle but immediately reseals itself when the needlehas been removed. The purpose of the patch is to permit the astronaut toinject himself with drugs or other medicines in the event he becomessick or is in pain during an Apollo flight.

FIG. 6 is an enlarged view of the right leg of the torso limb suitillustrated in FIG. 5 with parts broken away to show portions of thethigh and knee convolutes. Specifically, the thigh convolute cover 130awhich is sewn to the suit along its upper and lower edges, is brokenaway at 165 to show the thigh convolute 167. The convolute is molded andformed of a rubberized fabric to assume the natural shape of a convoluteor substantially constant volume bellows. Passing beneath cable guide138 and overlying the convolute is a metal wire or cable 168 secured atits lower end by eyelet 170 to a fabric reinforcement 172 sewn to thethigh cone 174. The other end of cable 168 is similarly attached abovethe bellows to the upper part of the leg by an eyelet indicated indashed lines at 176. A similar cable (not shown) overlies the bellows onthe inside leg surface, i.e., spaced approximately 180 around the legfrom cable 168. These two thigh cables form an elongation restraint forthe convolutes 166 so as to resist elongation of the convolutes when thesuit is inflated. The substantially constant volume nature of theconvolute permits the suit to be readily flexed in the area of the thighjoint even when under substantial internal pressure.

Knee convolute cover 134 is similarly broken away at 178 to show aportion of the knee convolute 180. The convolute is similar to the thighconvolute and is molded from a rubberized fabric and similarly isrestrained longitudinally by a pair of cables on opposite sides of theknee, one of which is illustrated in dashed lines at 182. The cable isjoined at its upper end by an eyelet 184 to reinforcement 172 and at itslower end by an eyelet 187 to the lower leg cone 188. Near the bottom ofthe lower leg cone is provided a loop tape 190 and slide fastener 192for joining the boot 161 of FIG. 5 to the leg of the torso limb suit.The urine transfer fitting 164 is shown as formed in the thigh cone 174as is the bio-medical injection patch 166.

FIG. 7 is a perspective view of the comfort liner assembly forming theinner layer of the torso limb suit of FIG. 5. The comfort liner,generally indicated at 194 in FIG. 7, covers the entire body with theexception of the head, hands and feet. It includes a neck portion 196with a snap flap 198 for the attachment of a communication lead for themicrophones 68 and of FIG. 2. Mounted on the shoulders of the liner area pair of cushion pads 200 and 202 and similar pads 204 and 208 areprovided on the upper arms. Sewn into the breast portion of the liner isa communications lead passthrough 210 and a bio-medical lead passthrough212. A somewhat similar water connector passthrough 214 is sewn to theleft breast of the liner. Fastener tapes are provided on the liner at216, 218, and 220, and a waste valve lead passthrough 222 is sewn intothe upper portion of the right leg. The fastener tapes, in conjunctionwith zippers 224 and 226 at the lower ends of the legs, are used toconnect the liner to the interior of the pressure garment assembly andspecifically to the interior of the torso limb suit of FIG. 5.

FIG. 8 shows the helmet half 228 of the helmet attaching ring assembly54 of FIG. 2. FIG. 9 shows the suit half of the helmet attaching ringassembly. The suit half 120 is formed of a metal housing 230 on which ismounted a vent channel 232, a resilient seal 234, and a locking ring236. On the upper surface of the locking ring are a pair of index marks238 and on the outside ofthe locking ring is a lock subassembly 240 anda lock stop 242. The helmet half 228 is similarly made of metal and isprovided with a vent channel 244 adapted to cooperate with the channel232 of the suit half 120 of the helmet attaching assembly. Similar indexmarks 246 are provided on the upper surface of the helmet half of theassembly. During assembly, the helmet half or ring 228 is telescopicallyreceived within the upper portion of the suit half or ring 120 and thevent channels are aligned by the index marks 238 and 246. The two ringsare then locked together by the lock subassembly 240 in tight sealingengagement.

FIG. 10 is an enlarged perspective view of the pressure helmet assembly52 of FIG. 2. The major portion of this assembly comprises a transparentshell of polycarbonate material attached at its lower end to the neckring 228 of FIG. 8. Mounted in the rear of the helmet is a vent pad 248having along its upper surfaces spacers 250 which space the upper end ofthe vent pad from the top of the helmet to provide gas channels 252communicating with gas passageways 253 through the vent pad. Pressurizedlife supporting gas (oxygen) is transmitted upwardly through thepassageways in the vent pad and exhausts through the channels 252 overthe head of the astronaut to impine upon the front area of the helmet'soas to prevent the helmet from fogging in front of the astronauts face.Mounted near the front of the helmet is a feed port 256 normally closedoff by feed port cover 258.

FIG. 11 shows the space suit electrical harness by means of which theastronauts physical condition is monitored and through which hecommunicates with other astronauts and with the space craft. Thebiomedical belt 96, which he wears around his waist and which isprovided with bio-medical sensors, is provided with an upwardlyextending noncrushable lead 260 which is electrically connected throughconnector 262 to an electrical harness 264. Approximately midway of theharness is an electrical jack 266 by means of which 'the astronaut isplugged into a suitable power supply,

either in the space craft or in the lunar module previously described,by means of a multiwire cable passing through the electrical connector66 of FIGS. 2 and 5. The upper end of the harness is electricallyconnected through connector 268 to the communications carrier 104 whichfits over the astronauts head. This harness includes a pair of earphones270 and 272, as well as the microphones 68 and 70 previously described,which el ements are embedded in or attached to the relatively softfabric padding material of the communications carrier. Electricalconnection to the harness from the micro-phones and earphones is by wayof a noncrushable flexible lead 274.

FIG. 12 is a perspective view of the rear of the outer covering orintegrated thermal micro-meteoroid garment 112 of FIG. 4 forming theouter component of the pressure garment assembly of the space suit. Thisgarment is designed primarily for heat insulation to protect theastronaut from the extremes of heat and cold in space and on the lunarsurface and also to protect the astronaut from micro-meteoroidbombardment. It consists of the integral boots 76 and 78 and covers theentire body with the exception of the hands and head. Ex-

tending from just below the neck is an entrance slidev fastener flap 276which covers the double slide fastener I through which the space suit isentered. This flap is partly broken away at 278 to show the snapassembly 280 and loop tape 282 for closing it and lacing garment 112 tothe torso limb suit assembly 114. A lumar module restraint strap 284 isattached over each hip and just above each knee is an assist strap 286.The outer cover garment 112 is of multilayer construction comprising alight colored reflective metallized outer shell and an inner linerseparated by several spaced layers of heat insulating material.

FIG. 13 is a perspective view of the pressure glove 72 of FIG. 4. Thisglove is provided with individual fingers 294 and a separate thumb 296,all formed integral with a hand covering sheath molded from a rubberizedfabric for good flexibility, i.e., Nylon dipped in a Neoprene compound.Preferably molded at the ends of the fingers and thumb are metal pieces(not shown) simulating finger nails to assist the astronaut inperforming intricate tasks with the hands. Overlying the rubberizedsheath and cemented to it is a fabric half glove 298 somewhat resemblingin appearance a golf glove and formed of fabric to provide restraint forthe rubberized fabric or bladder when the glove is inflated. Adjacentthe wrist, the half glove 298 is provided with a fastener tape 300 andover the top portion with an adjusting belt 302.

Glove 72 is provided with a convolute enclosed by cover 303 and isjoined to the space suit sleeve by a rotatable metal connector assemblyas described below. Restraint cables in the glove cooperate with cover303 to restrain the wrist convolute. The glove is molded to size from acast of the astronauts hand. Bladder projections 305 at the fingerjoints provide increased flexibility.

Adapted to be received over the pressure glove 72 of FIG. 13 is anextravehicular glove 38 shown in FIG. 14. This glove is preferably madeof good heat insulating material much in the manner of the integratedthermal micro-meteoroid garment of FIG. 12, and comprises an elongatedcuff 304 extending upwardly over the forearm so as to cover the pressurerelief valve 82 of FIG. 2. This glove too is provided with separatefingers 306 and a separate thumb (not shown). Sewn to the top of theglove is a flap 308. The extravehicular glove 38 is provided with anadjustable strap 310 for tightening it over the upper portion of theastronauts hand to provide restraint for the palm. Flap 308 is thenturned down over the adjustable strap 310 and secured above the wrist bycooperating hook and pile fasteners 312 on the auxiliary flap 313attached to the glove 38 by snap fasteners 314.

FIGS. 15 and 16 are perspective views of the left and right lunarovershoes 42 and 40, respectively. The lunar overshoes are of similarconstruction and each includes a donning strap 316 forming a loop at theheel which may be grasped by the astronaut to draw the heel of theovershoe over the space suit boot. Each overshoe tongue 318 is providedwith a snap fastener 320 cooperating with corresponding snaps 322 forconnecting the front of the overshoe to the tongue. Finally, theovershoe is secured over the instep by a strap assembly 324 fastened bya latch 326. The lunar overshoe provides both thermal (insulation) andabrasion protection for the astronauts foot on the lunar surface.

FIG. 17 is an enlarged view of the extravehicular visor assembly 20 ofFIG. 1. This visor comprises a collar 328 attachable to the neck of thespace suit and a semispherical base 330 adapted to protect theastronauts head both against physical damage and against intense heasand light from the sun. Base 330 is preferably a multilayer constructioncomprising an outer tough protective polycarbonate sheell and an innermembrane separated by several layers of heat insulating material. Thebase is cut away in the front as indicated by the dashed line at 332 sothat it may be slipped over the pressure helmet assembly 52 of FIG. 2.It is then attached to the neck of the space suit by means of a latchingmechanism (not shown) and the flexible fabric collar 328.

Along the cut away front portion of the base is a visor, generallyindicated at 334, comprising an outer rigid polycarbonate layer 336forming a sun visor and a spaced inner rigid layer 338 of transparentpolycarbonate forming a protective visor. The outer layer or sun visoris coated to provide light attenuation and to reduce heat gain withinthe helmet. It is provided with a tab 339 on each side so that it may bemoved between full up and full down positions. The visor is pivoted oneach side adjacent the astronauts ears to the base 330. One of thesupport pivot assemblies 340 is illustrated in cross section in FIG. 17Aand comprises a pivot pin 342 secured to the base and biased by a hingeadjustment spring 344. This spring bears against a friction plate 346and the two visors are spaced by washers 348 and a central spacer 350.The upper and lower edges of the visor are closed off by light sealsalong its upper and lower edges as illustrated at 352 in FIG. 17B and354 in FIG. 17C these figures respectively showing cross-sections of thecircled areas A and B in FIG. 17. Thus, when the astronaut closes thevisor assembly 334, he is completely protected both against physicaldamage and against the intense and ultraviolet radiation from the sunexisting in space and on the lunar surface. At the same time, each layeror shield 336 or 338 of the visor may be independently moved upwardly toany desired position and may be completely slid over the back of thevisor assembly about pivot pins 342 when the protection is not neededand the astronaut wishes to see through the helmet more clearly.

FIG. 18 is an enlarged view of the liquid cooling garment 98 of FIG. 3.This garment is worn by the astronaut underneath the pressure garmentassembly much in the manner of long underwear and is worn in conjunctionwith a pair of heavy socks 356 and 358 attached to it. The liquidcooling garment 98 may be worn by all the astronauts but is onlyrequired for extravehicular activity to provide liquid cooling when theastronaut is outside the space vehicle and exposed to the intense raysof the sun. The garment is provided at its front with a zipper 360through which it is donned and with snap fasteners 361 for securing toit the biomedical belt 96 of FIG. 3. A dosimeter pocket 362 is providedin the left leg of the garment and mounted on the waist is a water line364 comprising inlet and outlet pipes terminating at their upper ends ina double or two-way connector 366. This connector is adapted to passcooling water both into and out of the cooling garment by way of theconnector 64 of FIG. 2. The lower ends of the tubes 364 are connected toinlet and outlet manifolds respectively, generally indicated at 368,which in turn are coupled to Tygon tubing 370 which passes through thecooling garment and over substantially the astronauts entire body.

FIG. 19 is a diagrammatic view of the pressurization and ventilationsystem through the space suit of the present invention. Flow ofpressurized life supporting gas, such as oxygen, is indicated by thearrows in FIG. 19, the light arrows indicating inward flow and thedarker arrows showing the return gas flow paths. While a preferreddirection is illustrated, it is understood that the air flow, ifdesired, may be in the reverse direction. Oxygen may enter througheither one of the gas inlet connectors 56 or 58 since these connectorsare in fluid communication with each other by way of an intermediateplenum 372. A similar plenum 374 joins the gas outlet connectors 60 and62 so that the outlet may be taken from either of these connectors. Aredundant connector assembly is provided so that the astronaut mayattach one set of connectors to the lunar module before exiting from thespace vehicle without first having to disconnect the other set from thecabin supply. The double set of connectors is also provided so that theastronauts may be connected to each other in the event the supply to oneof them for some reason fails.

Gas passes upwardly from one of the inlet connectors 56 or 58 by way ofone of the noncrushable ducts 376 or 378 where it exists through ventchannel 244 in the helmet ring into the vent pad 248 of the helmet shownin FIG. and downwardly over the astronauts head onto the front surfaceof the helmet where it helps to defog the helmet in front of theastronauts face. The life supporting gas is, of course, also breathed bythe astronaut.

Incoming gas is also supplied from one of the inlet connectors to thetorso channels 380 and 382. These channels preferably are pervious togas along their length so that the gas is distributed to the astronautstorso over substantially the entire length of both the torso channels towhich the gas is supplied. Gas from the helmet and from the torso underpressure passes over the astronauts body and downwardly and outwardly ofthe limbs as indicated by the light arrows in the drawings. The gas isreturned from the hands by way of arm channels 384 and 386 and to therespective outlet connectors 60 and 62. Similarly, gas is returned fromthe feet by way of leg channels 388 and 390 to the outlet connectors 60and 62. The return channels 384, 386, 388 and 390 are vented adjacentthe extremities so that the return gas may enter them and be conductedto the outlets. Foot pads 392 and 394 are also provided to help collectthe returning gas and to ventilate the feet.

Thus, the life supporting gas (1) pressurizes the interior of the suitto a pressure of from 3 to 4 pounds per square inch, (2) provides abreathable gas to the astronaut, and (3) ventilates and helps cool thesuit and removes moisture resulting from perspiration over theastronauts entire body. Pressure gage provides the astronaut with avisual indication of the pressure within the suit and a pressure reliefvalve 82 automatically opens when the pressure becomes too high torelieve the pressure within the suit.

FIGS. 20 and 21 show the interconnecting locking rings for attaching apressure glove, such as the glove 72 of FIG. 4, to the suit. FIG. 20shows the suit half of the assembly, i.e., the suit ring at the wrist ofthe suit sleeve, and FIG. 21 shows the glove half or the metal ringattached to the glove. The suit ring is the female half and is generallyindicated at 396 in FIG. 20. It comprises a locking ring 400 on ahousing 402 to which is mounted a vent fitting 404. Locking ring 400 isprovided with a pair of lock tabs 406 and 408, a lock button 410, andindex marks 412 for aligning it with the glove ring of FIG. 21.

The glove ring is the male half and is generally indicated at 414 inFIG. 21. It consists of an outer race 416 on which is mounted a ventfitting 418 and an inner race 420. The rings of FIGS. 20 and 21 arealigned by index marks and locked together in sealtight relationship tojoin the gloves to the sleeves of the space suit. Th glove ring includesa sealed bearing with inner and outer races to permit 360 of gloverotation.

The torso limb suit 1 14 of FIG. 5 forms the basic garment since itprovides sealing over the greater part of the body to contain the lifesupporting gas and also incorporates restrain mechanisms so that theastronaut may move about and perform tasks. This torso limb suitassembly is a custom-sized unit which encompasses the body exclusive ofthe head and hands. The integrated thermal micro-meteoroid garment 112is laced to the torso limb suit 114 and acts as a shield for the torsoand limbs against the hazards of free space and lunar regions. Thepressure helmet assembly is constructed of clear polycarbonate plasticand, when secured to the torso limb suit 114, remains in fixed position.The pressure glove is basically a conformal molded bladder having aquick disconnect coupling, restraining features and is retained forintravehicle use only. The extravehicular glove provides thermalmicro-meteoroid protection layers that are slipped over the basicpressure glove assembly. The lunar overshoe is similar in cross sectionto the extravehicular glove and is donned prior to egress. The slip-onhelmet shield is a lightweight polycarbonate shell which fits over thepressure helmet assembly and provides scuff protection during tunneltransfer. The purge valve inserted into the helmet feed port is used topurge carbon dioxide from the helmet area during extravehicularoperations. Gas connector caps are installed in the nonutilized gasconnectors to prevent inadvertent depressurization as may be cuased bythe accidental opening of the water block within the connector. A suitdonning cloth strap assembly is inserted into the slide tab of each rearentry slide fastener assembly, i.e., an inner pressure sealing fastenerand an outer restraint slide fastener, at the back of the suit and thesestraps are used to facilitate actuation of the slide fasteners. The neckdam constructed of Neoprene fits around the neck and over the helmetattaching ring to prevent the entrance of water into the suit duringwater egress.

The torso limb suit 114 is an anthropomorphic pressure envelope whichencloses the torso and limbs of the astronaut, exclusive of the head andhands. The torso section is customsized to fit the individual while thelimb sections are graduated in sizes and feature lace adjustmentprovisions to accommodate individual limb lengths. Convoluted jointsnear constant volume are located at the shoulders, elbows, hips, knees,and ankles (as well as at the glove wrists) to permit joint movementswith a minimum of energy expenditure.

The suit is a gas retaining restraint assembly. lt incorporatesreinforced attachment supports for restraint cables which sustain axiallimb loads during pressurized modes of operation. The front of the suitemploys a block and tackle system having adequate mechanical advantageto permit the foreshortening of the torso during extended periodsofsitting or bending. An arm assembly is secured to each torso scyeopening. Axial loads across the shoulders are sustained by the shoulderrestraint cable assembly.

A wrist disconnect assembly is secured to the lower arm extremity andconsists of a mechanical self-sealing coupling designed to receive thepressure glove. A leg assembly is secured to the torso thigh opening.Axial loads at this joint are sustained by inner thigh crotch cables andouter thigh restraint cables. The thigh restraint cables are customlength and are designed to establish a proper crotch/limb angle whichaccommodates the wearers need for comfort and mobility. The leg assemblyends at midcalf where it interfaces with the boot assembly. The bootassembly encloses the foot and is flexible enough to allow some ankleand foot movements.

The innermost layer of the torso limb suit is a removable liner assemblywhich is designed to promote comfort and to facilitate donning the suit.A mechanical self-sealing coupling is installed in the torso neckopening and is held in place by means of a compression band. The inletand outlet gas connectors are attached to each side of the front torso.The dual or redundant connector installation permits an umbilicaltransfer between the ventilation systems of the space craftenvironmental control system, portable life supporting system, or teststand, without interrupting the flow of pressurization and ventilationgas through the suit. A balllock type quick disconnect multiple waterconnector assembly provides a dual passage through the suit forconnecting the liquid cooling supply to the liquid cooling garment. Whenthe liquid cooling garment is not connected, a plug is locked in placeto prevent leakage of gas out of the suit during pressurized modes ofoperation. The suit electrical harness provides an electrical interfacebetween the communications/bioinstrumentation components of the suit andthe communications/bio-instrumentation umbilical of the space craft,portable life support system, or test stand. A transfer hose connectedto the internal housing of the urine transfer connector interfaces withit for the transfer of urine to the waste management system of the spacecraft. The pressure gage provides for visual monitoring of thedifferential pressure. Mounted to the left wrist cone is a pressurerelief valve which relieves suit pressures in excess of 5.5 p.s.i.

The suit of the present invention is designed to afford pressurizedprotection for the astronaut during periods of extravehicular activityand in the space craft during pressurized modes of operation. Thecombination sealing and restraint structure of the suit accepts astandard operating pressure of 3.75 p.s.i.g. The assembly isstructurally tested at 6.0 p.s.i.g. and is periodically proof-tested at8.0 p.s.i.g. The suit is designed to withstand a burst pressure of notless than 10.0 p.s.i.g. Also, the pressurized envelope will not permitleakdage in excess of s.c.c. per minute when pressurized to 3.75p.s.i.g. under normal conditions. The gas flow into the helmet passesover the inside surface of the front of the helmet to facilitatehelmet'defogging and is then supplied to the oral-nasal area of thehelmet for efficient respiration and dissipation of carbon dioxide fromthat area. As the flow of gas passes down through the neck opening areaand over the body, the gas flow removes heat and transports evolved bodygases, toxicants, and moisture out of the suit. The normal inlet gasflow temperature is expected to be 35-85 F. During extravehicular modesof operation with the inlet gas connector diverter valves in the closedposition, the specified pressure drop across the ventilation system is anominal 2.273 inches of waer at 6.0 cubic feet per minute flow rate ofoxygen at 3.9 p.s.i.a. having an inlet gas temperature of 77 F. Duringintravehicular modes of operation with the inlet gas connector divertervalves in the open position, a nominal pressure drop of 4.7 inches ofwater will exist at 12.0 cubic feet per minute flow rate of oxygen at3.5. p.s.i.a. with an inlet gastemperature of 50 F. The liquid coolingsystem is designed as the primary mode for removing body heat fromwithin the suit during the performance of extravehicular mission tasks.During the circulation process, the heat within the suit is transferredto the liquid which returns through the outlet passage of the multiplewater connector to the lunar module for cooling or chilling.

The space suit of the present invention is designed so that trainedpersonnel may don all the equipment without assistance. The aid of atechnician or fellow crewman, however, does facilitate donning andinsures that the tasks are properly accomplished. After theundergarments are first plced on, a donning lanyard is attached to eachof the slide fateners, namely, the pressure sealing slide fastener andthe restraint slide fastener which overlies it. The astronaut thenassumes a sitting position and places the suit on his lap with the rearentry area open. With one hand the astronaut grasps the helmet attachingring and with the other hand grasps the suit donning lanyard. One footis placed into the suit and manipulated until the foot is inserted inthe boot. This may be facilitated by grasping the loop at the rear ofthe boot. This procedure is then repeated for the other foot. The suitis then pulled upward into proper position over the legs and well upinto the crotch. The hands are then inserted into the shoulderconvolutes and the head is lowered and positioned into the neck ringwhile simultaneously slipping the hands fully into the arms and throughthe wrist connectors. The astronaut then stands and permits the suit tosettle over the torso and limbs. One lanyard is then used to help closefirst the sealing slide fastener and then the restraint slide fatenerwhich overlies it. The various connections to the tubing, gloves andhelmet then follow in the proper order. in removing the suit, theprocedure is reversed.

It is apparent from the above that the present invention provides anovel space suit particularly designed to interface not only with cabinequipment but also portable equipment mounted on the astronauts back soas to render the astronaut completely self-supporting and mobile inhostile space and lunar surface environments. Important features of thesuit include an inner comfort liner to be worn over the undergarments,an intermediate principal garment incorporating both pressure sealingand mobility rstraints, and finally, an outer protective garment havingheat insulating and a metallized fabric outer layer. The suit coverssubstantially the entire body with the exception that it is providedwith readily removable gloves and helmet so that the astronaut may becompletely comfortable in the pressurized atmosphere of a space vehiclecabin.

The invention may be embodied in other specific forms without departingfrom the spirit or essential characteristics thereof. The presentembodiment is therefore to be considered in all respects as illustrativeand not restrictive, the scope of the invention being indicated by theappended claims rather than by the foregoing description, and allchanges which come within the meaning and range of equivalency of theclaims are therefore intended to be embraced therein.

What is claimed and desired to be secured by United States LettersPatent is:

1. A space suit for high altitude and space environments comprising apressure garment having an inner sealing bladder and an outer restraintconvering, a pair of like gas inlet connectors on said pressure garmentconnected together in substantially direct fluid connunication with eachother for selective use of either or simultaneous use of both inletconnectors for passing life supporting gas into said suit, a pair oflike gas outlet connectors on said pressure garment connected togetherin substantially direct fluid communication with each other forselective use of either or simultaneous use of both outlet connectorsfor passing gas as exhaust out of said suit, an electrical connector onsaid pressure garment for connection of communications andbioinstrumentation to the interior of the pressure garment, and aself-sealing biomedical injection patch on said pressure garment.

2. A space suit for astronauts comprising in combination: a conformalpressure garment having an inner sealing bladder and an outer restraintlayer, and outer thermal insulating garment over said pressure garment,

said pressure and thermal garments of said suit having torso and limbcovering portions adapted to cover an astronauts entire body except forhands and head, a transparent plastic helmet coupled to the neck of saidgarments, and a pair of pressure gloves rotatably coupled to the sleevesof said garments, said pressure garment including convoluted jointspositioned in said torso and limb covering portions to provide ease ofmobility when said pressure garment is worn, restraint cables secured tosaid pressure garment adjacent at least some of said convolutes toprevent elongation of said convolutes under internal gas pressure, apair of like connected together gas inlet connectors on the chest ofsaid pressure garment for passage into said suit of a life support gas,a pair of like connected together gas outlet connectors on the chest ofsaid pressure garment for passage out of said suit of gas as exhaust,electrical and cooling liquid connectors on said pressure garment and aself-sealing biomedical injection patch in said pressure garment.

3. A space suit according to claim 2 including a fecal containmentsystem, a bio-medical belt, and a urine collection transfer assemblywithin said pressure garment.

4. A space suit according to claim 2 including a liquid cooling garmenthaving cooling liquid inlet and outlet manifolds, flexible coolingliquid tubing passing through said liquid cooling garment and connectingsaid inlet and outlet manifolds, and a connector on said pressuregarment for passing liquid to said liquid cooling garment.

5. A suit according to claim 2 wherein said gloves comprise a bladderand an outer restraint fingerless glove, said bladder having individualfingers and thumb.

6. A suit according to claim 2 including boot portions and havingremovable thermal insulating gloves and overshoes received over the saidpressure gloves and boot portions of said suit.

7. A space suit according to claim 2 wherein each of said helmet,pressure gloves, neck and sleeves contain a metal ring, such ringsrespectively adapted for matingly coupling together said helmet withsaid neck and said pressure gloves with said sleeves.

8. A space suit for atronauts comprising an undergarment adapted tocover the astronauts entire body except for this head, an inner comfortliner, and outer thermal garment, and an intermediate pressure garmentcomprising an inner rubberized bladder and an outer fabric restraintlayer, said comfort liner, pressure garment and thermal garment beingintegrally joined and adapted to conform to the astronauts body,flexible joint portions in said suit adapted to fit over at least someof the locations of the astronauts joints when the suit is worn, sleeveportions in said suit, a pair of removable pressure gloves secured tothe said sleeve portions, a removable plastic helmet secured to the neckportion of said suit, a pair of inlet gas connectors operativelypositioned in said suit for supplying gas under pressure into theinterior of said suit, a pair of outlet connectors operativelypositioned in said suit for removing said gas therefrom as exhaust, aflexible hose system secured to the interior of said pressure garmentand operatively connected to said inlet gas connectors and to saidoutlet connectors for directing pressurized gas over the interior ofsaid suit, a conduit system in said suit communicating with said hosesystem for pass-

1. A space suit for high altitude and space environments comprising apressure garment having an inner sealing bladder and an outer restraintconvering, a pair of like gas inlet connectors on said pressure garmentconnected together in substantially direct fluid connunication with eachother for selective use of either or simultaneous use of both inletconnectors for passing life supporting gas into said suit, a pair oflike gas outlet connectors on said pressure garment connected togetherin substantially direct fluid communication with each other forselective use of either or simultaneous use of both outlet connectorsfor passing gas as exhaust out of said suit, an electrical connector onsaid pressure garment for connection of communications andbio-instrumentation to the interior of the pressure garment, and aself-sealing biomedical injection patch on said pressure garment.
 2. Aspace suit for astronauts comprising in combination: a conformalpressure garment having an inner sealing bladder and an outer restraintlayer, and outer thermal insulating garment over said pressure garment,said pressure and thermal garments of said suit having torso and limbcovering portions adapted to cover an astronaut''s entire body exceptfor hands and head, a transparent plastic helmet coupled to the neck ofsaid garments, and a pair of pressure gloves rotatably coupled to thesleeves of said garments, said pressure garment including convolutedjoints positioned in said torso and limb covering portions to provideease of mobility when said pressure garment is worn, restraint cablessecured to said pressure garment adjacent at least some of saidconvolutes to prevent elongation of said convolutes under internal gaspressure, a pair of like connected together gas inlet connectors on thechest of said pressure garment for passage into said suit of a lifesupport gas, a pair of like connected together gas outlet connectors onthe chest of said pressure garment for passage oUt of said suit of gasas exhaust, electrical and cooling liquid connectors on said pressuregarment and a self-sealing biomedical injection patch in said pressuregarment.
 3. A space suit according to claim 2 including a fecalcontainment system, a bio-medical belt, and a urine collection transferassembly within said pressure garment.
 4. A space suit according toclaim 2 including a liquid cooling garment having cooling liquid inletand outlet manifolds, flexible cooling liquid tubing passing throughsaid liquid cooling garment and connecting said inlet and outletmanifolds, and a connector on said pressure garment for passing liquidto said liquid cooling garment.
 5. A suit according to claim 2 whereinsaid gloves comprise a bladder and an outer restraint fingerless glove,said bladder having individual fingers and thumb.
 6. A suit according toclaim 2 including boot portions and having removable thermal insulatinggloves and overshoes received over the said pressure gloves and bootportions of said suit.
 7. A space suit according to claim 2 wherein eachof said helmet, pressure gloves, neck and sleeves contain a metal ring,such rings respectively adapted for matingly coupling together saidhelmet with said neck and said pressure gloves with said sleeves.
 8. Aspace suit for atronauts comprising an undergarment adapted to cover theastronaut''s entire body except for this head, an inner comfort liner,and outer thermal garment, and an intermediate pressure garmentcomprising an inner rubberized bladder and an outer fabric restraintlayer, said comfort liner, pressure garment and thermal garment beingintegrally joined and adapted to conform to the astronaut''s body,flexible joint portions in said suit adapted to fit over at least someof the locations of the astronaut''s joints when the suit is worn,sleeve portions in said suit, a pair of removable pressure glovessecured to the said sleeve portions, a removable plastic helmet securedto the neck portion of said suit, a pair of inlet gas connectorsoperatively positioned in said suit for supplying gas under pressureinto the interior of said suit, a pair of outlet connectors operativelypositioned in said suit for removing said gas therefrom as exhaust, aflexible hose system secured to the interior of said pressure garmentand operatively connected to said inlet gas connectors and to saidoutlet connectors for directing pressurized gas over the interior ofsaid suit, a conduit system in said suit communicating with said hosesystem for passing some of said gas directly to the front of saidhelmet, a communications carrier within said helmet, an electricalconnector on said suit, an electrical harness in said suit coupling saidelectrical connector to said communications carrier, convolutes at thejoint portions, restraint cables secured to said pressure garmentadjacent at least some of said convolutes to prevent elongation of saidocnvolutes under internal pressure, and means on said suit for attachingto it a portable life support module.
 9. A space suit according to claim8 including a block and tackle assembly secured to the front of saidsuit for assisting the astronaut in bending.
 10. A space suit accordingto claim 8 including a cable restraint assembly secured to said pressuregarment and passing through the crotch of said suit so as to resist theexpansion thereof.
 11. A space suit according to claim 8 wherein saidthermal garment comprises severl layers of insulation and a metallizedfabric outer layer, said thermal garment including a removable chestcover for covering said inlet and outlet connectors provided in saidpressure garment.